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 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

Date: February 1, 1944
Creator: Nitzberg, Gerald E.
Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine

Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine

Date: December 1, 1944
Creator: Desmon, Leland G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: July 1, 1943
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The development and application of high-critical-speed nose inlets

The development and application of high-critical-speed nose inlets

Date: July 1, 1945
Creator: Wright, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Mach number indicator for use in high-speed tunnels

NACA Mach number indicator for use in high-speed tunnels

Date: July 1, 1943
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

Date: March 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight

Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight

Date: May 1, 1944
Creator: Zalovcik, J. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Physical data on certain alloys for high temperature applications

Physical data on certain alloys for high temperature applications

Date: April 1, 1943
Creator: Rote, F B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High temperature characteristics of 17 alloys at 1200 and 1350 F

High temperature characteristics of 17 alloys at 1200 and 1350 F

Date: March 1, 1944
Creator: White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Date: January 1, 1945
Creator: Zimmey, Charles M. & Lappi, Viola M.
Description: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
Contributing Partner: UNT Libraries Government Documents Department
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